$\require{mediawiki-texvc}$
  • 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Combined bleed valve and annular diffuser for gas turbine inter compressor duct

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-006/18   
미국특허분류(USC) 60/039.07 ; 60/226.3
출원번호 US-0817332 (1997-03-17)
우선권정보 CA-2133793 (1994-10-06)
국제출원번호 PCT/CA95/005 (1995-10-05)
§371/§102 date 19970327 (19970327)
국제공개번호 WO-9611340 (1996-04-18)
발명자 / 주소
인용정보 피인용 횟수 : 32  인용 특허 : 0
초록

A multi-spool gas turbine engine of the type having an annular inter compressor duct connecting a low pressure compressor to a further compressor stage, and having improved bleed means for bleeding off a variable amount of air from the duct when the engine is being operated at partial load. The bleed means comprises opening means arranged circumferentially around the outer wall of the duct, and pivotally mounted air deflectors for deflecting air flowing in the duct outwardly through the openings in the outer wall of the duct. In accordance with the inven...

대표
청구항

[ I claim:] [1.] A multi-spool gas turbine engine having an inter compressor duct (10) connecting a low pressure compressor to a further compressor stage, of the kind in which there is provided bleed means (11,16) for bleeding off a variable amount of air from said duct, said duct being annular and having an inner wall (10b) and an outer wall (10a) and having a central axis, and in which said bleed means comprises opening means (11) arranged circumferentially around the outer wall of said duct and pivotally mounted air deflector means (16) for deflecting...

이 특허를 인용한 특허 피인용횟수: 32

  1. Stadler, Michael; Braeutigam, Ralf. Aircraft with an engine having a by-pass air inlet opening and a bleed air outlet. USP2018029902500.
  2. Siering, Jean-Marc. Apparatus and method for bleeding off compressor air in a jet engine. USP2016119506424.
  3. Boeck, Alexander. Arrangement for the cooling of the casing of an aircraft gas turbine engine. USP2004116817189.
  4. Cadieux, Michel. Bleed off valve system. USP2009097594403.
  5. Mårtensson, Hans; Nilsson, Martin. Bleed structure for a bleed passage in a gas turbine engine. USP2013098528344.
  6. Mårtensson, Hans; Nilsson, Martin. Bleed structure for a bleed passage in a gas turbine engine. USP2013078484982.
  7. Negulescu, Dimitrie. Bleed valve of a compressor, in particular a compressor of a bypass aero-engine. USP2003076588195.
  8. Appleby, Andrew; Kesner, Charles E.; Garrod, Todd C.; LaBenz, Joel E.. Bleed valve outlet flow deflector. USP2010097797945.
  9. Appleby,Andrew; Kincheloe,Todd A.; Facinelli,William A.; Reed,William H.. Bleed valve outlet flow deflector. USP2008067387489.
  10. Tokoro, Mario; Rekimoto, Junichi; Ayatsuka, Yuji; Tajima, Shigeru. Data communication system, data communication apparatus, and data communication method for generating or detecting an event. USP201509RE45705.
  11. Thies, Robert. Device for the extraction of bleed air and aircraft engine with at least one device for the extraction of bleed air. USP20190110174674.
  12. Loringer,Daniel Edward; Dillen,Eric Richard; Furman,Anthony Holmes; Swenson,Kendall Roger. Diffuser for centrifugal compressor. USP2006097101151.
  13. Smith, Darren M.; Brooks, Judith F.. Fan duct blocker actuation tab seal. USP2014128919784.
  14. Rice, Edward Claude; Bloom, Stuart; Louie, John R.. Flow splitter for gas turbine engine. USP2014098833087.
  15. Bradbrook, Stephen John; Davis, Brian; Wilson, Richard James. Gas turbine engine. USP2011027878005.
  16. Bradbrook, Stephen John; Davis, Brian; Wilson, Richard James. Gas turbine engine. USP2012028112983.
  17. Dougan, Jr., Donald; Carminati, Daniel; Wang, Cheng-Zhang. Gas turbine engine outer case with contoured bleed boss. USP2016129528391.
  18. Pritchard, Jr., Byron Andrew; Pezzi, Paul Alfred; Cunningham, III, George Gould; Moniz, Thomas Ory; Ross, Steven Alan; Holm, Raymond Gust. Gas turbine engine two degree of freedom variable bleed valve for ice extraction. USP2016129518513.
  19. Kupratis, Daniel Bernard; Moon, Francis R.. Gas turbine engine with stream diverter. USP2016129523329.
  20. Horner, Michael W.. Gas turbine in-line front frame strut. USP2003106637208.
  21. Venter, Gideon. Gas-turbine engine in particular aircraft engine. USP2012128336288.
  22. Pichel, Sacha. Gas-turbine engine with bleed-air tapping device. USP2015028944754.
  23. Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Elder, James S.. Integrated actuator module for gas turbine engine. USP2015089097137.
  24. Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Elder, James S.. Integrated actuator module for gas turbine engine. USP2012078210800.
  25. Ramachandran, Dhinagaran; Guntu, Sujatha; Kuchana, Vinayender; Srinivasan, Balamurugan; Gupta, Anish; Couey, Paul; McKeever, Craig; Malak, Malak; Muthiah, Gopal Samy. Inter-turbine ducts with guide vanes. USP2014098845286.
  26. Kuchana, Vinayender; Srinivasan, Balamurugan; Guntu, Sujatha; Malak, Malak Fouad; Couey, Paul; Mckeever, Craig. Inter-turbine ducts with variable area ratios. USP2017019534497.
  27. Carr,Robert Jonathan; Higgins,James Michael. Lift system for an aerial crane and propulsion system for a vehicle. USP2006127147183.
  28. Haugen, Christina Granger Morrissey; Fintel, Bradley Willis; Green, Brian Richard; Klasing, Kevin Samuel. Modular louver system. USP2016079399951.
  29. Ottow, Nathan W.; Cooper, Nathan J.. Rotary exhaust valve system. USP2017069689502.
  30. Eleftheriou, Andreas; Alecu, Daniel; Menheere, David. Turbine engine heat recuperator system. USP2015069068506.
  31. Schirtzinger, Gary A.; Wurzbacher, Lance; Orr, Joseph L.. Valve system for a gas turbine engine. USP2012108286416.
  32. Starr, Matthew J.. Variable pressure ratio compressor. USP2014108863529.